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Lift alleviation in travelling vortical gusts

Published online by Cambridge University Press:  05 April 2023

Y. Qian ,
Z. Wang Open the ORCID record for Z. Wang [Opens in a new window]  and
I. Gursul Open the ORCID record for I. Gursul [Opens in a new window]
Y. Qian
Affiliation:
University of Bath, Bath BA2 7AY, United Kingdom
Z. Wang
Affiliation:
University of Bath, Bath BA2 7AY, United Kingdom
I. Gursul*
Affiliation:
University of Bath, Bath BA2 7AY, United Kingdom
*
*Corresponding author. Email: i.a.gursul@bath.ac.uk
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Abstract

Lift alleviation by a mini-spoiler on aerofoils, unswept and swept wings encountering an isolated counter-clockwise vortical gust was investigated by means of force and velocity measurements. The flow separation region behind the spoiler remains little affected during the gust encounter. The maximum lift reduction is found for the static stall angle of attack. The change in the maximum lift during the gust encounter is approximately equal to that in steady freestream. The comparison with plunging aerofoils reveals that, for the same maximum gust and plunge velocity, the effectiveness of the mini-spoiler is much better in travelling gusts. This reveals the importance of the streamwise length scale of the incident gust. For the unswept wing, there is some three-dimensionality of the flow separation induced by the mini-spoiler near the wing tip. The magnitude of the lift reduction can be estimated using the aerofoil data and by making an aspect ratio correction for the reduced effective angle of attack. For the swept wing, the mini-spoiler can disrupt the formation of a leading-edge vortex induced by the incident vortex on the clean wing and can still reduce the maximum lift.

Keywords

lift alleviationmini-spoilergustswept wing
Type
Research Article
Information
The Aeronautical Journal , Volume 127 , Issue 1316 , October 2023 , pp. 1676 - 1697
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Copyright
© The Author(s), 2023. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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